Gas turbine combustor

Abstract

A combustor for a gas turbine having a centrally located fuel nozzle and inner, middle and outer concentric cylindrical liners, the inner liner enclosing a primary combustion zone. The combustor has an air inlet that forms two passages, each of which has a circumferential array of individually rotatable swirl vanes. The swirl vanes are mounted on axially oriented primary fuel pegs that extend through the air inlet passages. The middle and outer liners form an outer annular passage in which radially oriented secondary fuel pegs are disposed. The middle and inner liners form an inner annular passage that is supplied with cooling air. A perforated circumferentially extending baffle is locating in the inner annular passage and directs the cooling air to flow over the inner liner.

We claim: 
     
       1. In a gas turbine having a compressor for producing compressed air, a combustor for heating said compressed air comprising: a) a first substantially cylindrical liner forming a chamber therein for containing a combustion zone, a second substantially cylindrical liner forming an outer annular passage encircling said first liner;   b) a flow guide forming a first inlet passage having first and second portions, said first portion extending axially and being concentric with said liner, said second portion extending radially and encircling said first portion;   c) a plurality of fuel discharge means extending radially into said outer annular passage, each of said fuel discharge means having a plurality of fuel discharge ports formed therein;   d) a second inlet passage for said chamber, said second inlet passage having first and second portions, said first portion of said second inlet passage formed between said fuel nozzle and said flow guide and extending axially and being concentric with said first portion of said first inlet passage, said second portion of said second inlet passage extending radially and encircling said first portion of said second inlet passage;   e) a plurality of first swirl vanes disposed in said second portion of said first inlet passage; and   f) a plurality of second swirl vanes disposed in said second portion of said second inlet passage.   
     
     
       2. The combustor according to claim 1, further comprising means for rotating said first and second swirl vanes. 
     
     
       3. The combustor according to claim 1, further comprising a third substantially cylindrical liner enclosed by said second liner, said outer annular passage formed between said second and third liners, said first and second liners forming an inner annular passage therebetween. 
     
     
       4. The combustor according to claim 3, further comprising means for introducing cooling air into said inner annular passage. 
     
     
       5. The combustor according to claim 4, further comprising a circumferentially extending baffle disposed in said inner annular passage. 
     
     
       6. The combustor according to claim 5, wherein said baffle has means for directing cooling air introduced into said inner annular passage to flow over said first liner. 
     
     
       7. The combustor according to claim 6, wherein said baffle has means for reducing vibration of said inner liner. 
     
     
       8. The combustor according to claim 7, further comprising means for rotating said first and second swirl vanes. 
     
     
       9. In a gas turbine having a compressor for producing compressed air, a combustor for heating said compressed air comprising: a) a first liner forming a chamber therein for containing a combustion zone, a second liner encircling said first liner and a third liner enclosed by said second liner, an outer annular passage being formed between said second and third liners, and an inner annular passage being formed between said first and second liners;   b) a flow guide forming a first inlet passage having first and second portions, said first portion extending axially and being concentric with said liner, said second portion extending radially and encircling said first portion;   c) a centrally disposed fuel nozzle in fuel flow communication with said chamber;   d) a second inlet passage for said chamber, said second inlet passage having first and second portions, said first portion of said second inlet passage formed between said fuel nozzle and said flow guide and extending axially and being concentric with said first portion of said first inlet passage, said second portion of said second inlet passage extending radially and encircling said first portion of said second inlet passage;   e) a plurality of first swirl vanes disposed in said second portion of said first inlet passage; and   f) a plurality of second swirl vanes disposed in said second portion of said second inlet passage.   
     
     
       10. The combustor according to claim 9, further comprising means for rotating said first and second swirl vanes. 
     
     
       11. The combustor according to claim 9, further comprising means for introducing cooling air into said inner annular passage. 
     
     
       12. The combustor according to claim 11, further comprising a circumferentially extending baffle disposed in said inner annular passage. 
     
     
       13. The combustor according to claim 12, wherein said baffle has means for directing cooling air introduced into said inner annular passage to flow over said first liner. 
     
     
       14. The combustor according to claim 12, wherein said baffle has means for reducing vibration of said inner liner.